CN114526163B - Lubricating oil nozzle device and aircraft engine - Google Patents
Lubricating oil nozzle device and aircraft engine Download PDFInfo
- Publication number
- CN114526163B CN114526163B CN202210432793.9A CN202210432793A CN114526163B CN 114526163 B CN114526163 B CN 114526163B CN 202210432793 A CN202210432793 A CN 202210432793A CN 114526163 B CN114526163 B CN 114526163B
- Authority
- CN
- China
- Prior art keywords
- hole
- nozzle
- adjusting
- stepped
- oil
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000010687 lubricating oil Substances 0.000 title abstract description 27
- 238000007789 sealing Methods 0.000 claims abstract description 36
- 229920001971 elastomer Polymers 0.000 claims description 11
- 239000007921 spray Substances 0.000 claims description 3
- 238000002347 injection Methods 0.000 abstract description 19
- 239000007924 injection Substances 0.000 abstract description 19
- 239000003921 oil Substances 0.000 abstract description 17
- 238000004519 manufacturing process Methods 0.000 abstract description 9
- 238000001816 cooling Methods 0.000 abstract description 5
- 238000005461 lubrication Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 230000008685 targeting Effects 0.000 description 3
- 238000004026 adhesive bonding Methods 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 229920001973 fluoroelastomer Polymers 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000011295 pitch Substances 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 239000000243 solution Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Lubrication Of Internal Combustion Engines (AREA)
Abstract
The invention provides a lubricating oil nozzle device and an aircraft engine, wherein the lubricating oil nozzle device comprises: the nozzle base is provided with an oil inlet hole which is axially communicated; the nozzle flow and position regulator is provided with a stepped hole which is axially communicated, the nozzle base is connected with one end of the stepped hole, and the oil inlet hole is communicated with the stepped hole; the sealing gasket is arranged in the stepped hole, an adjusting through hole is formed in the sealing gasket, and the axis of the adjusting through hole is parallel to the axis of the stepped hole; the nozzle head is in threaded connection with the other end of the stepped hole and is abutted to the sealing gasket, the nozzle head is provided with an axial connecting hole and a nozzle hole, the nozzle hole is obliquely communicated with the axial connecting hole, the axial connecting hole is connected with the adjusting through hole, and when the nozzle head rotates, the flow area of the adjusting through hole and the axial connecting hole changes. The beneficial effects of the invention are as follows: the device is suitable for rapidly and accurately controlling the injection flow and the injection position of the lubricating oil required by the lubrication and cooling of the bearing of the aero-engine, the production rate is improved, and the production cost of the product is reduced.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a lubricating oil nozzle device and an aero-engine.
Background
Aviation gas turbine engine bearing operational environment is abominable, need lubricate and cool off it, in order to reach high-efficient lubrication and refrigerated while use the lubricating oil as few as possible, need carry out accurate control to lubricating oil flow and injection position.
Currently, nozzles and adjustment pads are often used to achieve precise control of the flow rate and location of the oil spray. In order to meet the requirement of oil supply flow required by lubrication and cooling, the aperture of the nozzle is calculated theoretically, and the aperture of the nozzle is smaller than the theoretically calculated aperture in diameter in general processing because the aperture is influenced by various factors such as the shape of the nozzle, the size of the nozzle, processing errors, the surface quality of an inner hole and the like, the theoretically calculated flow is usually inconsistent with the actual targeting experiment flow, when the flow targeting experiment result is inconsistent with the theoretically calculated result, the aperture of the nozzle needs to be corrected, if the aperture of the nozzle is smaller, the flow of the nozzle can meet the requirement through a hole expanding method, if the aperture of the nozzle is larger, the correction is more difficult, and the nozzle needs to be re-processed and corrected; in order to meet the requirement of an injection position, a nozzle hole is generally designed to form an included angle between the axial lead of the nozzle hole and an injection object, the axial movement of the nozzle is realized by adjusting the thickness of an adjusting pad, so that the injection position is adjusted, lubricating oil can be injected into an annular gap between a retainer and a bearing inner ring, and the effective lubrication and cooling of a bearing are realized.
The problems with the existing conventional oil nozzle structure are as follows:
1) due to the influence of a plurality of factors, the flow theoretically calculated by the lubricating oil nozzle is generally inconsistent with the actual targeting flow, the aperture size of the nozzle needs to be repeatedly corrected, the trial production period of a product is long, and even the nozzle cannot be corrected and reprocessed, so that the trial production cost is high;
2) in order to meet the requirement of accurate control of the injection position of the nozzle, a group of adjusting pads are required to be processed to adjust the oil supply position of lubricating oil, the trial production period of a product is long in the process of repeatedly disassembling and assembling the adjusting pads, and meanwhile, the oil supply position is changed due to the fact that the adjusting pads are easily mistakenly assembled in the guarantee maintenance process.
Disclosure of Invention
In view of this, embodiments of the present disclosure provide an oil nozzle device and an aircraft engine, so as to achieve the purpose of quickly achieving accurate control of the injection flow rate and the injection position of oil.
The embodiment of the specification provides the following technical scheme: an oil spray nozzle device comprising: the nozzle base is provided with an axially through oil inlet hole; the nozzle flow and position regulator is provided with a stepped hole which is axially communicated, the nozzle base is connected with one end of the stepped hole, and the oil inlet hole is communicated with the stepped hole; the sealing gasket is arranged in the stepped hole, an adjusting through hole is formed in the sealing gasket, and the axis of the adjusting through hole is parallel to the axis of the stepped hole; the nozzle head is in threaded connection with the other end of the stepped hole and is abutted to the sealing gasket, the nozzle head is provided with an axial connecting hole and a nozzle hole, the nozzle hole is obliquely communicated with the axial connecting hole, the axial connecting hole is connected with the adjusting through hole, and when the nozzle head rotates, the flow area of the adjusting through hole and the flow area of the axial connecting hole are changed.
Further, the nozzle base is in threaded connection with one end of the stepped hole.
Furtherly is provided with the rubber ring groove of circumference extension on the outer wall of nozzle base, and the lubricating oil nozzle device still includes the sealing washer, and the sealing washer setting can with the inner wall butt of the one end of shoulder hole in the rubber ring groove.
Furthermore, the nozzle base further comprises a locking assembly, the locking assembly is sleeved on the outer wall of the nozzle base, and the locking assembly can be matched with the nozzle flow and position regulator to lock the nozzle base and the nozzle flow and position regulator.
Further, one end of the stepped hole which is axially communicated is provided with a first cup-shaped locking ring, the locking assembly is a first prismatic boss which is fixedly arranged on the outer wall of the nozzle base, and the first cup-shaped locking ring can be locked on the periphery of the first prismatic boss.
Further, the adjusting through hole has the same or similar shape as the axial connecting hole.
Further, the shape of the adjusting through hole includes a kidney-shaped hole or a polygonal hole.
Furthermore, the other end of the stepped hole which is axially communicated is provided with a second cup-shaped locking ring, the outer wall of the nozzle head is provided with a second prism-shaped protruding part, and the second cup-shaped locking ring can be locked on the periphery of the second prism-shaped protruding part.
Furthermore, the axial connecting hole is an axial through hole, and a plug is arranged at one end, close to the nozzle hole, of the axial connecting hole.
The embodiment of the invention also provides an aircraft engine which comprises the lubricating oil nozzle device.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: the device is suitable for rapidly and accurately controlling the injection flow and the injection position of the lubricating oil required by the lubrication and cooling of the bearing of the aero-engine, the production rate is improved, and the production cost of the product is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic cross-sectional structural view of an embodiment of the present invention;
FIG. 2 is a schematic three-dimensional structure of a nozzle base in an embodiment of the invention;
FIG. 3 is a side view of FIG. 2;
FIG. 4 is a sectional view taken along line A-A of FIG. 3;
FIG. 5 is a schematic diagram of a nozzle flow and position regulator according to an embodiment of the present invention;
FIG. 6 is a sectional view taken along line B-B of FIG. 5;
FIG. 7 is a schematic view of a gasket according to an embodiment of the present invention;
FIG. 8 is a schematic view of the structure of an oil jet in the embodiment of the invention;
fig. 9 is a schematic diagram of the flow rate adjustment of the present invention.
Reference numbers in the figures: 1. a nozzle base; 11. an oil inlet hole; 12. a rubber ring groove; 13. a first prismatic projection; 2. a seal ring; 3. a nozzle flow and position regulator; 31. a thread relief groove; 32. a first cup-shaped locking ring; 33. a second cup-shaped locking ring; 34. a waist-shaped connecting hole; 4. a gasket; 5. a nozzle head; 51. an axial connecting hole; 52. a nozzle hole; 53. a second prismatic projection; 54. a plug hole; 6. and (7) a plug.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1 to 8, an embodiment of the present invention provides a lubricating oil nozzle device, including a nozzle base 1, a nozzle flow and position regulator 3, a sealing gasket 4 and a nozzle head 5, wherein the nozzle base 1 is provided with an oil inlet hole 11 which axially penetrates through; the nozzle flow and position regulator 3 is provided with an axially through stepped hole, the nozzle base 1 is connected with one end of the stepped hole, and the oil inlet hole 11 is communicated with the stepped hole; the sealing gasket 4 is arranged in the stepped hole, the sealing gasket 4 is provided with an adjusting through hole, and the axis of the adjusting through hole is parallel to the axis of the stepped hole; the nozzle head 5 is connected with the other end of the stepped hole in a threaded manner and abuts against the sealing gasket 4, the nozzle head 5 is provided with an axial connecting hole 51 and a nozzle hole 52, the nozzle hole 52 is obliquely communicated with the axial connecting hole 51, the axial connecting hole 51 is connected with the adjusting through hole, and when the nozzle head 5 rotates, the flow area of the adjusting through hole and the axial connecting hole 51 changes.
The flow area of the through hole and the axial connecting hole 51 is adjusted by screwing in or out the nozzle head 5, so that the lubricating oil injection flow required by adjusting the bearing is changed, the injection flow of the nozzle head 5 can be quickly and accurately controlled, and the aim of saving debugging time is fulfilled.
The nozzle base 1 is in threaded connection with one end of the stepped hole. And the nozzle flow and position regulator 3 and the nozzle base 1 are locked by a tool when the flow of the lubricating oil injected into the annular gap between the bearing inner ring and the retainer meets the requirement, so that the rapid and accurate control of the injection position of the nozzle is completed.
As shown in fig. 1 and 4, the outer wall of the nozzle base 1 is provided with a circumferentially extending rubber ring groove 12, the oil nozzle device further includes a sealing ring 2, and the sealing ring 2 is disposed in the rubber ring groove 12 and can abut against the inner wall of one end of the stepped hole.
In the embodiment of the invention, the rubber ring groove 12 and the sealing ring 2 are arranged, so that the nozzle flow and position regulator 3 and the nozzle seat 1 can be kept sealed when being arranged at the installation position, the leakage of lubricating oil is avoided, the normal injection pressure of the lubricating oil can be ensured, and the lubricating oil can be injected to the set position.
The sealing ring 2 is a fluororubber circular cross section rubber ring and plays a role of sealing lubricating oil, but the scheme does not limit the invention and is only one of the practical examples.
Preferably, the nozzle base 1 further comprises a locking assembly, the locking assembly is sleeved on the outer wall of the nozzle base 1, and the locking assembly can be matched with the nozzle flow and position regulator 3 to lock the nozzle base 1 and the nozzle flow and position regulator 3.
By arranging the locking assembly, the device provided by the embodiment of the invention can lock the nozzle base 1 and the nozzle flow and position regulator 3 when the preset flow and position are adjusted, so that the embodiment of the invention can continuously work, and secondary debugging is avoided.
Specifically, one end of the axially through stepped hole in the embodiment of the present invention is provided with a first cup-shaped locking ring 32, the locking component is a first prism boss 13 arranged on the outer wall of the nozzle base 1, and the first cup-shaped locking ring 32 can be locked on the periphery of the first prism boss 13, as shown in fig. 2, fig. 3 and fig. 5.
Of course, the embodiments of the present invention are not limited to the above-mentioned embodiments, and any embodiments that can lock the nozzle base 1 and the nozzle flow and position regulator 3 should be within the protection scope of the embodiments of the present invention.
The shape of the adjusting through hole is the same as or similar to that of the axial connecting hole 51 in the embodiment of the invention. Wherein, the shape of the adjusting through hole comprises a waist-shaped hole or a polygonal hole.
Preferably, the adjusting through hole and the axial connecting hole 51 are both kidney-shaped holes, as shown in fig. 8 and 9, by screwing the position of the axial connecting hole 51, the adjusting through hole and the axial connecting hole 51 can be smoothly changed at the position shown in fig. 9, so as to change the flow area between the adjusting through hole and the axial connecting hole, and achieve the purpose of flow rate adjustment.
It should be noted that the position shown in fig. 9 is only a reference position, and does not limit the present application.
As shown in fig. 5 and 8, the second cup-shaped locking ring 33 is provided at the other end of the stepped hole that penetrates in the axial direction, the second prismatic protrusion 53 is provided on the outer wall of the nozzle head 5, and the second cup-shaped locking ring 33 can be locked to the outer periphery of the second prismatic protrusion 53.
The second cup-shaped lock ring 33 has the same structure as the first cup-shaped lock ring 32, and is used for locking operation. Namely, when the position of the nozzle head 5 is adjusted to the set position, the nozzle head 5 is locked by the action of the second cup-shaped locking ring 33 and the second prism-shaped convex part 53.
It should be noted that the thickness of the lock ring of the first cup-shaped lock ring 32 is 0.5mm to 1mm, the length of the lock ring sleeve is 2mm to 5mm, and the inner cylindrical sealing surface is provided. The inner thread sections on the left side and the right side and the thread pitches of the inner thread sections are 0.5 mm-1.5 mm in the nozzle flow and position regulator 3, the inner sides of the two inner thread sections are correspondingly provided with thread escape grooves 31, and the thread escape grooves 31 on the right side are used for installing sealing gaskets 4. The two thread relief grooves 31 are connected through an axially arranged kidney-shaped connecting hole 34 (the size of the kidney-shaped connecting hole 34 depends on the flow requirement), as shown in fig. 1, 5, 6 and 7.
The sealing gasket 4 is a fluororubber gasket, the thickness is 1 mm-3 mm range, the appearance is circular, the middle part is a waist-shaped hole, the sealing gasket is assembled in a thread withdrawal groove 31 on the right side of the nozzle flow and position regulator 3, the waist-shaped hole on the sealing gasket 4 is aligned with the waist-shaped hole of the nozzle flow and position regulator 3, the sealing gasket is tightly pressed by screwing out a nozzle head 5 in the thread on the right side of the nozzle flow and position regulator 3, the compression ratio of the sealing gasket 4 is ensured to be between 10% and 35%, and the sealing gasket is used for preventing lubricating oil between the nozzle flow and position regulator 3 and the nozzle head 5 from leaking.
Preferably, as shown in fig. 1 and 8, the axial connecting hole 51 is an axial through hole, one end of the axial connecting hole 51 close to the nozzle hole 52 is provided with a plug hole 54, and a plug 6 is fixedly arranged in the plug hole 54. The plug 6 is arranged in a plug hole 54 of the nozzle head 5 and is in interference fit, and during assembly, glue is coated on the cylindrical surface of the plug 6 and is used for sealing lubricating oil.
The assembly steps of this embodiment are as follows:
step one, gluing and assembling the cylindrical surface of the plug 6 into a plug hole 54 of the nozzle head 5, and then punching three points to prevent the plug 6 from falling off;
secondly, gluing one side of the end face of the sealing gasket 4 and installing the sealing gasket into the nozzle flow and position regulator 3, wherein the glued side is close to the right end face of the kidney-shaped hole of the nozzle flow and position regulator 3, and the kidney-shaped hole of the sealing gasket 4 is ensured to be aligned with the kidney-shaped hole of the nozzle flow and position regulator 3;
step three, screwing the nozzle head 5 provided with the plug 6 into the nozzle flow rate and internal thread at the right end of the position regulator 3 provided with the sealing gasket 4, and ensuring the compression rate of the rubber gasket at the initial assembly position to be about 20% through calculation of a size chain;
step four, the sealing ring 2 is arranged in a rubber ring groove 12 of the nozzle base 1;
and step five, assembling the assembly assembled in the step three onto the assembly assembled in the step four, namely screwing the left internal thread of the nozzle flow and position regulator 3 onto the external thread of the nozzle base 1. And finally, preliminarily assembling the lubricating oil nozzle device with adjustable jet flow and jet position of the aero-engine.
The invention also provides an aircraft engine which comprises the lubricating oil nozzle device, and other parts of the aircraft engine are conventional parts in the prior art, and are not described again.
The beneficial effects of the invention are as follows: the precise control of the lubricating oil injection flow and the injection position required by the lubricating and cooling of the bearing of the aero-engine can be ensured, and meanwhile, compared with the traditional lubricating oil nozzle device, the precise control device can greatly shorten the adjustment time of the injection flow and the injection position, shorten the production period, avoid the repeated processing of the nozzle and save the production cost.
It should be understood that the above description is only exemplary of the invention, and is not intended to limit the scope of the invention, so that the replacement of equivalent elements or equivalent changes and modifications made in the present invention should be included within the scope of the present invention. In addition, the technical characteristics can be freely combined with each other, the technical characteristics can be freely combined with the technical scheme, and the technical scheme can be freely combined with the technical scheme.
Claims (8)
1. An oil spray nozzle device, comprising:
the nozzle comprises a nozzle base (1) provided with an oil inlet hole (11) which is axially communicated;
the nozzle flow and position regulator (3) is provided with a stepped hole which is axially communicated, the nozzle base (1) is connected with one end of the stepped hole, and an oil inlet hole (11) is communicated with the stepped hole;
the sealing gasket (4) is arranged in the stepped hole, an adjusting through hole is formed in the sealing gasket (4), and the axis of the adjusting through hole is parallel to the axis of the stepped hole;
the nozzle head (5) is in threaded connection with the other end of the stepped hole and is abutted against the sealing gasket (4), the nozzle head (5) is provided with an axial connecting hole (51) and a nozzle hole (52), the nozzle hole (52) is obliquely communicated with the axial connecting hole (51), the axial connecting hole (51) is connected with the adjusting through hole, and when the nozzle head (5) rotates, the flow area of the adjusting through hole and the axial connecting hole (51) changes;
nozzle base (1) with the one end threaded connection of shoulder hole, nozzle base (1) still include locking Assembly, locking Assembly cover is established on the outer wall of nozzle base (1), just locking Assembly can cooperate with nozzle flow and position control ware (3) in order to lock nozzle base (1) and nozzle flow and position control ware (3).
2. Oil nozzle device according to claim 1, characterized in that a circumferentially extending rubber ring groove (12) is provided on the outer wall of the nozzle base (1), the oil nozzle device further comprising a sealing ring (2), the sealing ring (2) being provided in the rubber ring groove (12) and being capable of abutting against the inner wall of one end of the stepped bore.
3. The oil nozzle device as claimed in claim 1, wherein one end of the axially through stepped bore is provided with a first cup-shaped locking ring, the locking assembly is a first prismatic boss (13) fixedly arranged on the outer wall of the nozzle base (1), and the first cup-shaped locking ring can be locked on the periphery of the first prismatic boss (13).
4. Oil nozzle device according to claim 1, characterized in that the adjusting through hole is the same or similar in shape to the axial connecting hole (51).
5. The oil nozzle device according to claim 4, wherein the shape of the regulation through hole includes a kidney-shaped hole or a polygonal hole.
6. Oil nozzle device according to claim 1, characterized in that the other end of the axially through stepped bore is provided with a second cup-shaped locking ring, and the outer wall of the nozzle head (5) is provided with a second prismatic protrusion, the second cup-shaped locking ring being lockable to the outer circumference of the second prismatic protrusion.
7. Oil nozzle device according to claim 1, characterized in that the axial connection hole (51) is an axial through hole, and the end of the axial connection hole (51) close to the nozzle hole (52) is provided with a plug (6).
8. An aircraft engine, characterized in that it comprises an oil nozzle device according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210432793.9A CN114526163B (en) | 2022-04-24 | 2022-04-24 | Lubricating oil nozzle device and aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210432793.9A CN114526163B (en) | 2022-04-24 | 2022-04-24 | Lubricating oil nozzle device and aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114526163A CN114526163A (en) | 2022-05-24 |
| CN114526163B true CN114526163B (en) | 2022-07-26 |
Family
ID=81627929
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210432793.9A Active CN114526163B (en) | 2022-04-24 | 2022-04-24 | Lubricating oil nozzle device and aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114526163B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114963923A (en) * | 2022-06-09 | 2022-08-30 | 哈尔滨东安实业发展有限公司 | Functional gauge for detecting nozzle oil inlet hole of aircraft engine and using method thereof |
| CN116044981B (en) * | 2023-02-07 | 2025-06-03 | 中国航发湖南动力机械研究所 | Embedded aircraft engine gearbox lubrication nozzle and gearbox |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4020982A (en) * | 1975-10-10 | 1977-05-03 | Leeds And Micallef | Rotary shut-off nozzle |
| CA1208923A (en) * | 1983-06-03 | 1986-08-05 | James S. Kelm | Flow modifying device |
| US5722778A (en) * | 1996-01-24 | 1998-03-03 | Ebara Corporation | Bearing device for vertical rotating machine |
| CN204328273U (en) * | 2014-12-11 | 2015-05-13 | 中航商用航空发动机有限责任公司 | The connection locking structure of a kind of oil pipe and pipe joint |
| CN106594248A (en) * | 2016-12-12 | 2017-04-26 | 中国燃气涡轮研究院 | Multipoint radial jetting oil supply nozzle for high-speed and heavy-load bevel gear |
| CN110325283A (en) * | 2017-02-08 | 2019-10-11 | Oem集团有限责任公司 | Flow rate adjustable nozzle system |
| CN110608283A (en) * | 2019-09-27 | 2019-12-24 | 吉林大学青岛汽车研究院 | Lubricating device for needle roller bearing and lubricating oil supply control method |
| WO2020114803A1 (en) * | 2018-12-03 | 2020-06-11 | BMTS Technology GmbH & Co. KG | Turbocharger with a hydrodynamic slide bearing, or hydrodynamic slide bearing |
| CN112177779A (en) * | 2020-10-20 | 2021-01-05 | 中国航发沈阳发动机研究所 | Lubricating oil nozzle with filtering function |
| CN213658233U (en) * | 2020-10-29 | 2021-07-09 | 西安成立航空制造有限公司 | Auxiliary device for testing flow of lubricating oil nozzle |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH10231753A (en) * | 1997-02-19 | 1998-09-02 | Ishikawajima Harima Heavy Ind Co Ltd | Gas flow control device in solid fuel gas generator |
| US8272218B2 (en) * | 2008-09-24 | 2012-09-25 | Siemens Energy, Inc. | Spiral cooled fuel nozzle |
| US8201758B2 (en) * | 2009-08-28 | 2012-06-19 | Globe Union Industrial Corp. | Fluid spraying device |
| GB201103261D0 (en) * | 2011-02-25 | 2011-04-13 | Mahle Int Gmbh | A bearing arrangement |
| CN202165575U (en) * | 2011-06-21 | 2012-03-14 | 中国航空动力机械研究所 | Lubricating oil spray nozzle and transmission gearbox provided with same |
| CN103775668B (en) * | 2013-04-27 | 2014-12-24 | 广州海鸥卫浴用品股份有限公司 | Jet flow valve element |
| FR3022587B1 (en) * | 2014-06-23 | 2019-03-22 | Safran Aircraft Engines | DEVICE AND METHOD FOR LUBRICATING A TURBOMACHINE BEARING BEARING |
| DE102016106376A1 (en) * | 2016-04-07 | 2017-10-12 | Hammelmann GmbH | High-pressure rotor nozzle |
| JP2018194111A (en) * | 2017-05-18 | 2018-12-06 | いすゞ自動車株式会社 | Lubricating device of transmission |
-
2022
- 2022-04-24 CN CN202210432793.9A patent/CN114526163B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4020982A (en) * | 1975-10-10 | 1977-05-03 | Leeds And Micallef | Rotary shut-off nozzle |
| CA1208923A (en) * | 1983-06-03 | 1986-08-05 | James S. Kelm | Flow modifying device |
| US5722778A (en) * | 1996-01-24 | 1998-03-03 | Ebara Corporation | Bearing device for vertical rotating machine |
| CN204328273U (en) * | 2014-12-11 | 2015-05-13 | 中航商用航空发动机有限责任公司 | The connection locking structure of a kind of oil pipe and pipe joint |
| CN106594248A (en) * | 2016-12-12 | 2017-04-26 | 中国燃气涡轮研究院 | Multipoint radial jetting oil supply nozzle for high-speed and heavy-load bevel gear |
| CN110325283A (en) * | 2017-02-08 | 2019-10-11 | Oem集团有限责任公司 | Flow rate adjustable nozzle system |
| WO2020114803A1 (en) * | 2018-12-03 | 2020-06-11 | BMTS Technology GmbH & Co. KG | Turbocharger with a hydrodynamic slide bearing, or hydrodynamic slide bearing |
| CN110608283A (en) * | 2019-09-27 | 2019-12-24 | 吉林大学青岛汽车研究院 | Lubricating device for needle roller bearing and lubricating oil supply control method |
| CN112177779A (en) * | 2020-10-20 | 2021-01-05 | 中国航发沈阳发动机研究所 | Lubricating oil nozzle with filtering function |
| CN213658233U (en) * | 2020-10-29 | 2021-07-09 | 西安成立航空制造有限公司 | Auxiliary device for testing flow of lubricating oil nozzle |
Non-Patent Citations (1)
| Title |
|---|
| 航空发动机电驱动滑油泵控制算法研究;黄果等;《燃气涡轮试验与研究》;20171215(第06期);全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114526163A (en) | 2022-05-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114526163B (en) | Lubricating oil nozzle device and aircraft engine | |
| US6776360B2 (en) | Spray gun with improved needle shut-off valve sealing arrangement | |
| US9593654B2 (en) | Injector sleeve | |
| US11644118B2 (en) | Electronic expansion valve | |
| US5275337A (en) | High pressure limiting valve with fast response and fuel injector equipped therewith | |
| US9175789B2 (en) | Pressure regulating valve | |
| CN114193321A (en) | Hydraulic expansion mandrel | |
| US7513116B2 (en) | Gas turbine engine fuel injector having a fuel swirler | |
| EP0921304B1 (en) | Fuel injection nozzle | |
| CN116213340A (en) | Tool and equipment for cleaning low-pressure air inlet on wing of aero-engine | |
| US11753958B2 (en) | Device for cooling an outer casing of a turbomachine and turbomachine provided with such a device | |
| US9631664B2 (en) | Bolted joint inner thread coating and methods of manufacturing | |
| CN115041914B (en) | Repairing method for inner hole of casing and casing | |
| CN217784570U (en) | High-pressure fluid plunger hole plate improved structure capable of reducing internal leakage | |
| JPH1172063A (en) | Fuel injection valve | |
| US8814222B2 (en) | Self-sealing tube for a gas turbine secondary air system | |
| US6824082B2 (en) | Method of producing a fuel injector, and relative fuel injector | |
| US9551242B2 (en) | Rocker arm for engines | |
| CN221236784U (en) | Mounting structure of igniter of miniature turbojet engine | |
| CN220850889U (en) | Pressure regulating valve | |
| CN115163960B (en) | An improved structure of a high-pressure fluid plunger orifice plate capable of reducing internal leakage | |
| CN216289495U (en) | Solid outer sealing washer, spark plug body, spark plug and vehicle engine | |
| CN218780406U (en) | Cooling nozzle for engine piston | |
| CN218982928U (en) | Anti-necking punch | |
| CN219932276U (en) | Axial clearance adjustment structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |